Propeller

ABSTRACT

A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.

TECHNICAL FIELD OF THE INVENTION

The invention relates to propellers that may be used, for example, foraircraft, watercraft, turbines, unmanned aerial vehicles and aircirculation devices.

SUMMARY

Embodiments of the invention provide a propeller that has a plurality ofblades and a means for generating non-axial lift, which createsnon-axial fluid flow, and a means for redirecting non-axial fluid flowto create axial fluid movement or thrust. The propeller may include ahub or be of a rim or “hubless” form. The plurality of blades eitherextends outward from the hub or inward from the rim. Each blade may forma loop-type structure that may be open or closed, and having an intakeportion, and exhaust portion and a tip portion extending radiallyoutward from to the hub or inward from a rim or “hubless” form. Themeans for generating non-axial lift and non-axial fluid flow to createaxial thrust may be a configuration of the blades wherein in across-sectional-profile of each of the plurality of blades, the distancefrom the rotational axis to the leading edge of the blade is greaterthan the distance from the rotational axis to the trailing edge of theblade in at least part of the tip portion.

The blades may have an intake portion, an exhaust portion, and a tipportion that connects the intake and exhaust portions, but is notnecessarily a discrete component. The propeller has an intake root andan exhaust root, which are at either the rim or hub, for example. Thetip portion may include a roll angle of ninety degrees, wherein a rollangle of zero is at the intake root. The tip portion vertical angle andpitch angle may be positive throughout. In an exemplary embodiment thetip portion produces more non-axial lift than either the intake or theexhaust portion.

In an illustrative embodiment the transition from the intake portion tothe tip portion occurs when the amount of non-axial lift produced by agiven parameter section of the blade is greater than the axial liftproduced.

DESCRIPTION OF THE DRAWINGS

For further detail regarding illustrative embodiments of the disclosedpropeller, reference is made to the detailed description provided below,in conjunction with the following illustrations: All figures are ofillustrative embodiments of the disclosed propeller.

FIGS. 1A-E depict various views of an illustrative propeller.

FIG. 2 depicts a parameter sections defining a propeller blade.

FIG. 3 depicts a blade parameter section geometry.

FIGS. 4A-F depict measurements of rake for parameter sections in theintake portion, tip portion and exhaust portion of a propeller blade.

FIGS. 5A-F depict measurements for skew angle and vertical angle ofparameter sections in the intake portion, tip portion and exhaustportion of a propeller blade.

FIG. 6 depicts an example fluid flow around propeller blades.

FIGS. 7A-D depict examples of alpha and radius values for selectedparameter sections.

FIGS. 8A-H depict illustrative values or relative values of variousparameters that define a parameter section or a blade.

FIGS. 9A-F depict pitch angles for selected parameter sections of theblades.

FIGS. 10A-B depict views of a turbofan.

FIG. 11 depicts an unmanned aerial vehicle.

FIGS. 12A-C depict roll angle for selected parameter sections.

FIGS. 13A-G depict a propeller without a hub and having a ring fromwhich propeller blades extend.

FIGS. 14A-B depict a two blade propeller and a cross-section thereof.

FIGS. 15A-B depict a three blade propeller and a cross-section thereof.

FIGS. 16A-B depict a five blade propeller and a cross-section thereof.

FIGS. 17A-B depict a seven blade propeller and a cross-section thereof.

FIGS. 18A-G depict an illustrative embodiment of a propeller with a highrake.

FIGS. 19A-G depict a further illustrative embodiment of a propeller witha high rake for intake and exhaust.

FIGS. 20A-I depict an inboard propeller.

FIGS. 21A-G depict a propeller with a through hub exhaust.

DETAILED DESCRIPTION OF THE INVENTION

FIGS. 1A-E depict propeller 100 according to an illustrative embodiment.FIG. 1A depicts a perspective view of propeller 100. FIG. 1B depicts aside view of propeller 100, and FIG. 1C depicts the opposing side ofpropeller 100. FIGS. 1D and 1E depict a top (fore) view and bottom (aft)view, respectively, of Propeller 100. Propeller 100 includes a pluralityof blades 102, 104, 106, each having, an tip portion 122, an intakeportion 124 and an exhaust portion 126. In this illustrative embodiment,blades 102, 104 and 106 extend from a hub 128. Each of blades 102, 104,106 has a median line 108, 110, 112, respectively. Blades 102, 104, 106rotate about hub axis 103. For simplicity the term “hub” may be used toinclude any rotational axis, even if there is no physical hub.

The blades have a means for generating non-axial lift and non-axialfluid flow and a means for redirecting the non-axial fluid flow to axialfluid flow. In illustrative embodiments, the means for generatingnon-axial lift and non-axial fluid flow is the configuration of the tipportion of the blade, which will be described further below. Inillustrative embodiments the means for redirecting the non-axial fluidflow to axial fluid flow is the configuration of the tip and intakeportion, and may also include the exhaust portion, which will also bedescribed in more detail below.

The term “propeller” as used herein may include rotary blade devicesthat can be used to displace fluid to propel an apparatus, or which areemployed in a stationary device such as, for example, a cooling or otherair circulating fan, which moves fluid such as air through or around it.

Propeller 100 has three blades 102, 104, 106 disposed at equalincrements around hub 128. Disclosed embodiments of the propeller mayhave for example, two, three, four, five, six, seven or eight bladesthat rotate in the same plane. The number of blades will generallydepend on the application of the propeller. For example, additionalblades may be beneficial for increases in the weight of a boat orairplane in which the propeller is employed to increase the area of theblades, thereby reducing the blade loading.

Blades 102, 104, 106 may be configured to rotate about an axiscorresponding to hub axis 103, but in an apparatus in which there is nohub, such as in a configuration in which the blades extend inward from arotating support. The rotation of the support may be generated by anelectromagnetic field. Hub 128 may also be hollow, and may have openingsin its surface, such as in a centrifugal fan.

FIG. 2 depicts a blade 200 having parameter sections 1-29, withparameter section 1 in the vicinity of the intake root 204, andparameter section 29 in the vicinity of exhaust root 206. Each parametersection represents a set of physical properties or measurements whosevalues determine the characteristics of the blade area. The parametersections as a group determine the shape of blade 200 and its behavior.Parameter sections are equally spaced in an exemplary embodiment but maybe selected at unequal intervals. FIG. 2 serves merely to illustrate howblade parameter sections may be laid out to define the blade geometry.Parameter sections represent the shape and orientation of blade 200 at aparticular place along the blade. A smooth transition is formed betweenparameter sections to create a blade. As used herein “orientation” mayinclude location. In the illustrative embodiment in FIG. 2, bladesections 1-29 are planar sections disposed along an irregular helicalmedian line 202. “Irregular helix” is used herein to mean varying from amathematical helix-defining formula or as a spiral in 3-D space whereinthe angle between the tangent line at any point on the spiral and thepropeller axis is not constant. The blade may have an irregular,non-helical median line at least in part, or the median line may be anirregular helix throughout.

Although 29 blade sections are shown in FIG. 2, more or fewer sectionscan be used to define a blade. Additionally, sections may exist withinor partially within the hub that are not shown or fully shown. Bladesmay be defined by planar or cylindrical parameter sections.

Parameter sections 1-29 are defined, for example, by orientationvariables, such as roll angle and vertical angle (alpha), and mayinclude location variables; and shape variables, such as chord length,thickness, and camber. Additional illustrative orientation or locationvariable include rake, skew angle and radius. Some or more of thevariables may change through the blade or a blade portion and some maybe constant throughout. Orientation variables may be measured withrespect to an X-Y-Z coordinate system. The X-Y-Z coordinate system hasthe origin at the shaft centerline and a generating line normal to theshaft or hub axis 103. The X-Axis is along hub axis 103, positivedownstream. The Y-Axis is up along the generating line and the Z-Axis ispositive to port for a right handed propeller. A left handed propelleris created by switching the Z-Axis and making a left hand coordinatesystem.

Parameter sections may be located by their chord (nose-to-tail)midpoint, such as by using radius, rake and skew. Parameter sections maybe oriented using the angles Phi, Psi and Alfa, as will be describedfurther below.

FIG. 3 depicts blade parameter section geometry by reference to across-sectional profile of a blade, which could be a parameter section.An illustrative parameter section 300. Parameter section 300 is in theform of an asymmetrical airfoil. The airfoil is bounded by a curvedblade surface line 302 and a generally flat blade surface line 304, witha rounded nose 306 at the leading edge 310 of the parameter section anda pointed or less rounded tail 308 at the trailing edge 312 of parametersection 300. Parameter sections may also be in the shape of asymmetrical airfoil. Additional parameter section shapes include, forexample, a shape having parallel blade surface lines 302, 304. Bladesurface lines 302, 304 may also be linear and at an angle to oneanother. The nose and tail edges may both be rounded, both be flat(perpendicular to one or both blade surface lines 302, 304) or one ofeither the nose or tail may be rounded and the other of the two flat. Ablade formed of a sheet material, for example, would generally exhibitparallel blade surface lines 302, 304. In an illustrative example of ablade formed of a sheet, the leading edge of the blade is rounded andthe trailing edge is flat or less rounded, though both intake andtrailing edges could be rounded.

Illustrative Shape Variables for Parameter Sections are Defined asFollows;

Radius: The term radius is used to define both the shape of a parametersection and its orientation with respect to the X-Y-Z coordinate system.With regard to the parameter section shape, radius may refer to thecurvature of the nose 306 of parameter section 300, for example, andthus will be referred to as a “nose radius.”. Other points on parametersection 300 may be used to calculate a radius. By way of example,parameter section leading edge radius may be calculated based on maximumthickness 316 and the length of chord 314.

Chord: The chord is the nose-to-tail line 314 of the parameter section.

Thickness: Various thickness measurements may define a parameter sectionsuch as, for example, the maximum thickness 316. A further illustrativeexample is the trailing edge thickness, which may be calculated as apercentage of maximum thickness 316. For example, the trailing edgethickness may be 8% of maximum thickness 316 of parameter section 300.

Camber: Camber 318 defines the curvature of a parameter section.

Illustrative Orientation Variables Include:

Rake: Rake is the axial location of a parameter section chord midpoint.

By “axial location” it is meant in this instance, along the X-axis,which is coincident with the propeller rotational axis. Illustrativerake measurements are shown in FIGS. 4A-F for various parametersections. Each of FIGS. 4A-F show coordinates X, Y and Z, wherein theX-axis is coincident with the propeller rotational axis, and the Y-axisand Z-axis are perpendicular to the X-axis, and the three axes aremutually perpendicular. Parameters are measured from the origin of thecoordinate system. In an illustrative embodiment, the zero point of thecoordinate system is along the propeller rotational axis, and is closerto the intake root than the exhaust root. Illustratively, values alongthe X-axis toward the intake root are negative and toward the exhaustroot are positive. In general a coordinate system is located as desiredand all parameters or geometry are measured from the origin of theselected coordinate system.

FIGS. 4A and 4B depict Rake for parameter sections 412, 414 on theintake portion 402 of blade 400. Parameter section 412 in FIG. 4A istoward tip portion 404 of blade 400. Parameter section 414 is towardintake root 406. Rake is measured along the propeller rotational axis oralong a line parallel to the rotational axis. In the illustrativeexamples of FIGS. 4A, 4B, Rake is the distance from point A at X equalszero to the X coordinate value of point B, wherein point B is at themidpoint 410 of the chord of parameter sections 412, 414. TheX-coordinate value of point B is represented by Bx in FIGS. 4A-F. Chordsof parameter sections shown in FIGS. 4A-F are defined by end points 408,416.

FIGS. 4C and 4D depict Rake for parameter sections 418, 420 on the tipportion 404 of blade 400. Parameter section 418 in FIG. 4C is at a firstposition in tip portion 404 of blade 400 wherein the roll value(described further below) is greater than zero and less than 90 degrees.Parameter section 420 in FIG. 4D is at a second position in tip portion404 where the roll value is equal to or greater than 90 degrees. In theillustrative examples of FIGS. 4C, 4D, Rake is the distance from point Aat X equals zero to the X coordinate value, B_(x), of point B, whereinpoint B is at the midpoint 410 of the chord of parameter sections 418,420. FIGS. 4E and 4F depict Rake for parameter sections 422, 424 on theexhaust portion 426 of blade 400. Parameter section 422 in FIG. 4E istoward tip portion 404 of blade 400. Parameter section 424 is towardexhaust root 428. In the illustrative examples of FIGS. 4E, 4F, Rake isthe distance from point A at X equals zero to the X coordinate value ofpoint B, wherein point B is at the midpoint 410 of the chord ofparameter sections 422, 424.

Pitch Angle: Pitch Angle is the angle between the chord line of aparameter section and a plane perpendicular to the X-axis. Pitch anglemay be calculated based on pitch distance and blade radius. Examples ofpitch angle of parameter sections is provided in FIGS. 4A and 4C. FIGS.4A and 4C show pitch angle for parameter sections 412 and 418,respectively.

Radius: The orientation radius is the distance from the hub center 208to the midpoint 320 of chord 314 of a parameter section. Chord 314 mayalso be referred to as the nose-to-tail line. The radius described inthis paragraph will be referred to as the parameter section orientationradius to differentiate it from the nose radius or other parametersection shape radii, which are not measured with respect to the X-Y-Zcoordinate system. Midpoint 320 of chord 314 is the point on theparameter section chord line through which the median line 202 wouldpass. This is illustrated in FIG. 2 by line R which extends from hubcenter 208 to the midpoint of the chord of parameter section 5. Notethat the chord of parameter section 5 and its midpoint are notspecifically shown in FIG. 2.

FIGS. 5A-F depict blade 400 viewed along the blade rotational axis X.FIGS. 5A-F identify representative parameter section radii and skewangle. FIG. 5A depicts the radius of parameter section 412 in the intakeportion 402 of blade 400. FIG. 5B shows the radius of parameter section414, a parameter section in intake portion 402 of blade 400 further fromintake root 406 than parameter section 412. FIGS. 5C and 5D depict radiifor parameter section 418 and 420, respectively, wherein parametersection 418, 420 are in tip portion 404. FIGS. 5E and 5F depict radiifor exhaust parameter section 422 and 424, respectively, both withinexhaust portion 426. The position of parameter sections 412, 414, 418,420, 422 and 424 as being in intake portion 402, tip portion 404, orexhaust portion 426 are provided only for ease of discussion. The actualparameter values and resulting fluid flow may define the positions ofthe sections otherwise.

FIGS. 5A-F further show skew angle of parameter sections 412, 414, 418,420, 422, 424. Skew angle is the projected angle from a line throughmidpoint 410 of chord 314 to the generating line, in this illustrativeembodiment the Y-axis looking along hub axis 103 (X-axis).

FIGS. 7A-D, in addition to depicting skew angle and radius, depictparameter section vertical angle, Alpha, labeled on each of FIGS. 7A-D.Vertical angle may also be referred to as “lift angle.” Alpha is theangle that the parameter section is rotated relative to a lineperpendicular to the skew line, which is identified in FIGS. 6A-D anddescribed below. The aforementioned skew line refers to the linetogether with the zero skew line that forms the skew angle. Depending onthe value of Alpha, the nose of the parameter section will either be“lifted” or will “droop” from a line perpendicular to the skew line thatforms the skew angle with respect to the zero skew line, wherein thezero skew line is coincident with the Y-axis of the coordinate systemidentified on FIGS. 7A-D.

It is noted that FIGS. 5A-F do not identify Alpha, because Alpha equalszero. When Alpha is zero, the chord line of the parameter section isperpendicular to the zero skew line. This can be seen by a comparison ofFIGS. 5A-F with FIGS. 7A-D.

Roll: Roll is the angle that a parameter section is rotated about itschord line. As described herein, a zero roll value is in a planeparallel to the hub axis. In an illustrative embodiment, roll at intakeroot 132 is zero, roll at exhaust root 134 is 180 degrees and a roll of90 degrees is at a location within tip portion 122.

Various illustrative embodiments will be described by combinations ofcharacteristics. The disclosed propeller includes different combinationsof the characteristics, equivalents of the elements and may also includeembodiments wherein not all characteristics are included.

In an illustrative embodiment of a propeller, the propeller includes aplurality of blades in a loop form, generally as shown in FIGS. 1A-E.The propeller in FIG. 1A is referred to only as a general reference toequate particulars with propeller regions. The actual form of thepropeller blades will vary according to the parameters and within theranges specified.

Each blade 102, 104, 106 of propeller 100 includes a tip portion 122, anintake portion 124 and an exhaust portion 126. In an illustrativeembodiment, the intake portion is 0-45% of the blade, the tip portion is30%-75% of the blade and the exhaust portion is 50 percent to 90 percentof the blade.

Propeller 100 may have various number of blades, each preferably withthe same characteristics and parameters, although variations betweenblades is within the scope of the embodiments. An illustrative number ofblades is between two and twelve, although more blades may be includedin a single propeller. In particular embodiments a propeller may havethree, four, five, seven or eleven blades. In a propeller embodimenthaving looped blades, the blades have an intake root 132 at hub 128 andan exhaust root 134 at hub 128. Intake portion 124, tip portion 122 andexhaust portion 126 together may form a closed loop or the loop may beopened at the intake “root” or exhaust “root.”

Roll: The roll angle (Psi) is the orientation angle about chord 314, forexample. Referring back to FIGS. 1A-F, intake portion 124 extends fromhub 128 generally outward for a propeller with a hub 128. Intake portion124 may have a roll of zero at intake root 132. Intake portion 124 isconfigured to create axial lift only or more axial lift than non-axiallift. The roll value for all parameter sections in intake portion 124may be zero. Illustrative roll value ranges for parameter sections inintake portion 124 include zero at intake root 132 progressing tobetween about 1 degree to 35 degrees where intake portion 124transitions to tip portion 122. Additional ranges of roll value forintake portion 124 from intake root 132 to tip portion 122 include: fromzero to between about 5 degrees to 25 degrees, and from zero to betweenabout 10 degrees to 20 degrees.

Tip portion 122 may also be defined by a tip portion intake end thatbegins at the first deviation from zero of roll value and extends to atip portion exhaust end that begins at a roll value of 90 degrees orjust greater than 90 degrees.

Tip portion 122 is configured to generate non-axial lift only, morenon-axial lift than axial lift, or more non-axial lift than intakeportion 124. The roll value of parameter sections in tip portion 122will transition from less than 90 degrees to greater than 90 degrees.Illustrative roll value ranges of tip portion 122 include between 1degree and 46 degrees at the transition from intake portion 124 throughbetween 91 and 150 degrees where tip portion transitions to exhaustportion 126. Additional illustrative roll value ranges of tip portion122 include beginning at the transition from intake portion 124, between5 degrees and 25 degrees and transitioning to a roll of between 110-135degrees.

In an illustrative embodiment the transition from intake portion 124 totip portion 122 occurs when the amount of non-axial lift produced by agiven parameter section is greater than the axial lift. In a particularembodiment of the invention this transition takes place when roll is 45degrees, or when roll is in a range of 40 degrees to 50 degrees.

Exhaust portion 126 is configured to generate less non-axial lift thantip portion 122. In an illustrative embodiment of the invention, theblade is configured so the average non-axial lift is the greatest in tipportion 122 as compared to either intake portion 124 or exhaust portion126. In an illustrative embodiment the blade is configured so theaverage non-axial lift, if any, is greater in exhaust portion 126 thanin intake portion 124. Illustrative roll value ranges of exhaust portion126 include between 91 degrees and 150 degrees at the transition fromtip portion 122 to exhaust portion 126 through 180 degrees at exhaustroot 134. Additional illustrative ranges include beginning at thetransition from tip portion 122, between 91 degrees and 135 degrees andtransitioning to a roll of 180 degrees at exhaust root 134.

FIGS. 8A-H depict illustrative values or relative values of variousparameters that define a parameter section or a blade. FIG. 8A depictsillustrative roll values from an intake root of a blade to exhaust root.In an illustrative embodiment, beginning at intake root 132 throughexhaust root 134, parameter section roll transitions from about zero to5 degrees over the first 25 percent of the blade, from about 5 degreesto about 162 degrees over the next 50 percent of the blade, and fromabout 165 degrees to about 180 degrees over the last 25 percent of theblade.

In an illustrative embodiment non-axial lift is created by 10 percent to90 percent of the blade. Further illustrative ranges include 10 percentto 75 percent and 25 percent to 50 percent.

FIG. 6 depicts an illustrative example of a propeller 600 showing fluidflow around blades 602, 604. Intake portions 606, 608 show fluid flow inan axial direction at the intake portions 606, 608 of blades 602, 604,respectively. Fluid flow remains axial as the propeller moves forward orfluid moves through blades 602, 604. Fluid flow is still axial as itdeparts from the exhaust portions 614, 616 of blades 602, 604,respectively.

Within the tip portion of blades 602, 604 axial thrust is generated fromthe non-axial lift. Non-axial lift results in a fluid flow into thepropeller blade, such as within the interior of the loop. Fluidencounters the leading edge of tip portions 610, 612 non-axially. Asfluid is pulled in by the tip portions 610, 612 it is redirected intotoward an axial direction within the loops of blades 602, 604. Thenon-axial lift may cause drag, which is created by the tip portion. Asfluid passes the trailing edge of blades 602, 604, in tip portions 610,612 it is in an axial direction or more toward an axial direction thanwhen it entered the interior of the loops of blades 602, 604.

In an illustrative embodiment, propeller 600 is configured to createmixture of the free stream and jet stream of fluid flow aft of thepropeller, wherein the mixing area is greater than the diameter of thepropeller, wherein the propeller diameter in this instance is themeasurement of the largest span of the propeller through the hub axis.

Referring back to FIGS. 1A-F, tip portions 122, intake portions 124 andexhaust portions 126 do not necessarily extend equal distances, such asalong median lines 108, 110, 112. In an illustrative embodiment, intakeportions 124 encompass a shorter distance than exhaust portions 126.Therefore, the distance along median line 108, 110, 112 wherein theblade is configured to redirect axial lift to non-axial lift extends agreater distance from exhaust root 134 than from intake root 132. In anillustrative embodiment, intake portion 124 extends a distance in arange of 10 percent to 50 percent of the median line length, exhaustportion 126 extends a distance in a range of 10 percent to 60 percent ofthe median line length; and tip portion 122 extends a distance of 5percent to 60 percent of the median line length.

FIG. 8B depicts illustrative relative pitch angle values from an intakeroot of a blade to exhaust root. In an illustrative embodiment,beginning at intake root 132 through exhaust root 134, parameter sectionpitch angle transitions from about 70 degrees to about 35 degrees, overthe next 50 percent of the blade pitch angle transitions from about 35degrees to about 25 degrees, and over the last 25 percent of the blade,pitch angle transitions from about 25 degrees to about 75 degrees. In anillustrative embodiment of the invention, tip portion 122 has a non-zeropitch angle throughout. In an exemplary embodiment of the invention tipportion 122 is defined as and is configured to have non-zero pitch andredirect non-axial lift to create axial thrust.

FIG. 8C depicts the vertical angle, Alpha, from an intake root of ablade to exhaust root according to an illustrative embodiment. Thevertical angle orients parameter sections away from being perpendicularto skew. In an illustrative embodiment the vertical angle is zero forall parameter sections. In a further embodiment the vertical angle forthe intake and tip portions is positive for all parameter sections andthe vertical angle for the exhaust portion is negative for all parametersections. In yet a further embodiment tip portion 122 may have at leastone parameter section with a non-zero vertical angle. In otherembodiments, the average vertical angle for the tip and intake portionsis greater than the average vertical angle of the exhaust portion.

In an illustrative embodiment the average vertical angle for parametersections in exhaust portion 126 is greater than the average verticalangle for parameter sections in intake portion 124.

Illustrative ranges of the vertical angle of tip portion 122 includes, 0to 1 degree, 1 degree to 10 degrees; 4 degrees to six degrees; zero to 5degrees; 1 degree to 4 degrees; and 2 degrees to 3 degrees. The verticalangle may also be zero throughout the entire blade. The vertical angleat the tip may cause fluid to be drawn in to the interior of the blade“loop” and may thereby cause drag. The vertical angle at the tip mayalso create fluid flow that is off-axis from the direction of travelwhich is redirected to axial fluid flow within the loop. The greater thevertical angle in the tip region, the greater the amount of non-axiallift and as a result the greater the amount of non-axial fluid flow intothe propeller. The vertical angle of parameter sections in tip portion122 may create non-axial lift and drag in the vicinity. In illustrativeembodiments, the vertical angle is between −45 degrees and 45 degreesthroughout the blade; between −25 degrees and 25 degrees or between −15degrees and 15 degrees throughout the blade.

FIG. 8D depicts illustrative relative radius values from an intake rootof a blade to exhaust root. In an illustrative embodiment the radius ofparameter sections increases throughout the first 60 percent to 80percent of the blade beginning at intake root 132 and then decreasesthrough parameter sections through to exhaust root 134. As used in thisparagraph and elsewhere, parameters transitions over parameter sectionscorrespond to transitions through the blade.

FIG. 8E depicts illustrative rake values from an intake root of a bladeto exhaust root. Rake in an exemplary embodiment may be increasinglynegative from intake root 132 through the first 30 percent to 40 percentof the blade. Rake may then increase for the next 10 percent to 15percent of the blade until it reaches positive values. Rake may thencontinue to increase for an additional 20 percent to 40 percent of theblade and then level off for the remainder of the blade or decrease.Rake may also be linear from the intake root of position of zero to apositive exhaust root value.

FIG. 8F depicts illustrative relative skew values from an intake root ofa blade to exhaust root. In an illustrative embodiment the skew valuecontinually increases from intake root 132 through exhaust root 134. Inanother illustrative embodiment the skew value may continually decreaseso the exhaust portion is forward of the intake and tip portion on itsrotational plane. Parameter section chord 314 may be normal to the skewline throughout the blade or in a portion of the blade, wherein the skewline to which chord 314 is perpendicular is the skew line that forms theskew angle with the zero skew line.

FIG. 8G depicts illustrative relative camber values from an intake rootof a blade to exhaust root. In an illustrative embodiment the camber ofparameter sections transitions from a positive value at the intake root132 to a negative value at the exhaust root 134, wherein the suctionside of the blade changes to the pressure side of the blade near thetransition from the tip portion to the exhaust portion at the interfaceof positive camber to negative camber.

FIG. 8H depicts illustrative relative chord values from an intake rootof a blade to exhaust root. In an illustrative embodiment chorddecreases from intake root 132 and then begins to increase towardexhaust portion 126 and continues to increase to exhaust root 134. Inother illustrative embodiments, chord increases from intake root 132 andthen decreases toward exhaust portion 126 and continues to decrease toexhaust root 134.

In illustrative embodiments tip portion 122 from the tip portion intakeend to the tip portion exhaust end exhibits one or more of the followingcharacteristics:

-   -   average non-axial greater than average axial lift;    -   non-axial lift from the tip portion intake end to the tip        portion exhaust end;    -   zero alpha value throughout;    -   positive pitch angle throughout;    -   positive pitch distance throughout    -   positive pitch angle throughout a portion between 70% and 95% of        tip portion 122    -   a maximum blade radius value within the tip portion extending        from a parameter section having a roll value of 80 degrees to a        parameter section having a roll value of 95 degrees.

The chart below provides illustrative values for selected parametersections. The parameter sections are 2, 6, 11, 19, 25 and 29 from ablade defined by 30 parameter sections. Parameter section 2 is theclosest of the selected parameter sections to intake root 132. Parametersection 29 is the closest of the selected parameter section to exhaustroot 134.

Section & Figure Radius Pitch Pitch Angle Numbers (inches) (inches)Skew° (Phi) Roll (Psi) SECT. 2 0.860 9.899 3.139 61.38 0.57 FIG. 5ASECT. 6 2.000 9.396 12.615 36.79 3.34 FIG. 5B SECT. 11 3.278 9.36625.043 24.45 11.98 FIG. 5C SECT. 19 4.335 10.248 46.069 20.62 91.38 FIG.5D SECT. 25 2.674 11.197 62.206 33.68 172.24 FIG. 5E SECT. 29 0.94112.035 73.241 63.85 178.62 FIG. 5F

FIGS. 5A-F provide a schematic representation of parameter sections 2,6, 11, 19, 25 and 29, respectively. As noted above, FIGS. 5A-F depictparameter sections having an Alpha value of zero. In an illustrativeembodiment these parameter sections may be part of a group of parametersection all having a zero alpha value that form a propeller blade.

Referring to FIGS. 5A-F, it can be seen that the radius increases fromparameter section 2 through parameter section 19 and then is decreasingat parameter section 25 through parameter section 29. Pitch, skew androll increase throughout parameter sections 2, 6, 11, 19, 25 and 29.Pitch angle decreases from parameter section 2 through parameter section25 and then shows an increase at parameter section 29.

FIGS. 9A-F provide a schematic representation of pitch angle forparameter sections 2, 6, 11, 19, 25 and 29, respectively. Pitch anglevaries throughout the blade with the largest values occurring at theintake and exhaust roots.

FIGS. 7A-D depict representations of parameter sections 6, 11, 19 and 25of 30 parameter sections defining a blade shown in the table below.These parameters include varying Alpha values. The chart below providesillustrative values for the selected parameter sections.

Section & Vertical FIG. Radius Pitch Pitch Angle Roll Angle Numbers(inches) (inches) Skew° (Phi) (Psi) (Alpha) SECT. 6 2.000 9.396 12.61536.79 3.34 16.74 FIG. 7A SECT. 11 3.278 9.366 25.043 24.45 11.98 16.34FIG. 7B SECT. 19 4.335 10.248 46.069 20.62 91.38 11.75 FIG. 7C SECT. 252.674 11.197 62.206 33.68 172.24 −14.80 FIG. 7D

Radius, Pitch, Skew, Pitch Angle and Roll are given the same values asthe illustrative example having Alpha equal to zero. In the embodimentrepresented by FIGS. 7A-D Alpha decreases through parameter sections 6through 19 and then becomes negative at a location on the blade betweenparameter section 19 and 25. This change is illustrated in FIGS. 7A-D.

It is noted that throughout where values are associated with sectionparameters, the values may define blade portions as each of the intake,tip and exhaust portions are defined herein.

Illustrative embodiments of the propeller may have one or more of thefollowing characteristics and any characteristics described herein:

-   -   throughout at least a portion of tip portion 122 on the intake        side 90 degree roll, the distance (N) to the nose of a parameter        section as measured perpendicularly from hub axis 103 is greater        than the distance (T) to the tail of the parameter section as        measured perpendicularly from the hub axis;    -   80% of the tip portion has a roll value of less than 90 degrees        and N>T for the same 80% of the tip portion;    -   average pitch angle of exhaust portion 126 is greater than the        average pitch of intake portion 124;    -   pitch angle varies as roll varies;    -   pitch angle is positive throughout the blade;    -   length of entire leading edge of propeller blade is greater than        the length of the entire trailing edge as measure        perpendicularly from the propeller axis;    -   first rake position (intake root) is less than the last (exhaust        root) rake position thus there is a resulting gap between the        intake root and the exhaust root with the exhaust root aft of        the intake root;    -   skew increases from intake root 132 to exhaust root 134;    -   intake root is forward of exhaust root and skew begins at zero        and ends at a positive value;    -   intake root is aft of exhaust root and skew starts at zero and        ends at a negative value;    -   the entire intake portion is forward of the exhaust portion        except for tip region.    -   the greatest thickness of the blade cross-section is between the        midpoint of the chord and the leading edge of the cross-section;    -   the pressure face continues to turn toward the tip on the intake        portion and then becomes suction face on the exhaust portion;    -   intake root 132 is in-line with exhaust root 134 so skew is        zero;    -   substantial mixing of jet stream and free stream downstream of        the exhaust blade compared to traditional propellers;    -   blades are configured to “effectively increase” the diameter of        the propeller by increasing mixture of free stream and jet        stream;    -   pitch angle of the exhaust blade at its root end is greater than        the pitch angle of the intake blade at its root end;    -   the tip portion has a 90 degree roll angle closer to the exhaust        portion than to the intake portion;    -   a gap between the intake portion root and the exhaust portion        root;    -   chord length of parameter sections varying throughout the        blades;    -   parameter sections defining the blade are planar and        perpendicular to the median line;    -   Some or all of the parameter sections defining the blade are        non-planar, cylindrical to the median line.    -   negative rake in the exhaust portion;    -   positive rake in the exhaust portion and    -   blades of different configuration are incorporated into a single        propeller.

Propeller variations can have the same median line but vary in otherparameters. A series of propellers according to illustrative embodimentsof the invention can be based on a common median line with varyingparameter section pitch, angle of attack, angle, rake, surface area,area ratio, spline form, cross-sectional profile, chord length, verticalangle, roll and other blade parameters.

FIGS. 14A-B, 15A-B, 16A-B and 17A-B depict side views andcross-sectional views of propellers with two blades, three blades, fourblades and seven blades, respectively. Cross-sections are taken viewedfrom the propeller fore location along the rotational axis. Thecross-sections are generally in tip portion 122 of the blade. As canbeen seen in each of the cross-sectional drawings, for eachcross-sectional profile of the blade, the distance A from the rotationalaxis to the leading edge of the blade cross section is greater than thedistance B from the rotational axis to the trailing edge of the bladecross section in these particular areas of tip portion 122. In anillustrative embodiment of the invention A is greater than B for all oftip portion 122. In further illustrative embodiments of the invention Ais greater than B for 50 percent to 100 percent of tip portion 122. In afurther embodiments the percent of tip portion 122 that has A greaterthan B is in the range of 85 percent to 90 percent. In general, thegreater the difference between the length of A band B the more fluidwill be pulled in from a non-axial direction. Similarly, the greater thepercent of the blade that has A greater than B, the more fluid will bepulled in from a non-axial directions.

Illustrative embodiments have been depicted or described as a propellerhaving a hub. The blades described herein may also be used in a hublesspropeller device such as shown in FIGS. 13A-G. FIG. 13A is a perspectiveview of a “hubless” propeller 800. In this embodiment there are sevenblades 804, each having their intake root 132 and exhaust root 134extending from a rim 802, with tip portion 122 toward the center of thepropeller. FIGS. 13B-G show views from the top, bottom, “front,” “back,”“left,” and “right,” respectively. The terms “left,” “right,” “front”and “back” are used for description purposes only to distinguish viewsfrom 90 degree intervals around the propeller, but as a circular device,have no literal meaning. The blades follow the same or similarcharacteristics as propellers with hubs, with some varied air flow dueto the rim.

Further disclosed is a method for creating a propeller according to anyof the embodiments described herein. In an exemplary embodiment aplurality of independently modifiable orientation and shape variablesare provided to define the orientation and shape of a plurality ofparameter sections forming a propeller blade. The shape and orientationvariables can be any combination of those disclosed herein. Theparameter sections may be planar or cylindrical. In an illustrativeembodiment the variables are modified to direct and redirect lift asdesired, such as described herein. The configured parameter sections arethen used to form a blade by extrapolating between parameter sections toform smooth lines. The method may be used to form any blade as describedherein.

The invention includes several different devices having the disclosedpropeller incorporated therein. For example, the invention includes thefollowing illustrative devices: propulsors, shrouded propellers, encasedpropellers, impellers, aircraft, watercraft, turbines, including windturbines, cooling devices, heating devices, automobile engines, unmannedaerial vehicles, turbofans (hydrojets), air circulation devices,compressors, pump jets, centrifugal fans, jet engines and the like. Theinvention also includes methods of manufacturing and designing apropeller, including any of the above-listed devices, according to anyof the embodiments described, pictured or claimed herein; a method ofmanufacturing a device comprising any of the aforementioned propellers;a method of manufacturing a product wherein the method includesinstalling a device containing any of the aforementioned propellers.

The ratio of the roll to distance along the median line may be a factorin whether a particular propeller is suitable for an application. Forexample, a greater roll per given distance creates a more squat bladeprofile and thus may be more suitable for application as a fan for acooling or ventilating device.

In an illustrative embodiment, a propeller as described herein isincorporated into a turbofan as shown, for example, in FIGS. 10A and10B. The turbofan may have, for example, between eight and twelveblades. It is noted that the blades depicted in FIGS. 10A-B are notnecessarily of a type described herein. The figures are merely providedto indicate the type of device.

In a further illustrative embodiment of the invention a propeller asdescribed herein is incorporated into an unmanned aerial vehicle ordevice such as shown for example, in FIG. 11. It is noted that theblades depicted in FIG. 11 are not necessarily of a type describedherein. The figures are merely provided to indicate the type of device.

Various embodiments and view of illustrative propellers are provided inFIGS. 18A-G, FIGS. 19A-G, FIGS. 20A-I and FIGS. 21A-G. Views includingfrom the top, bottom, “front,” “back,” “left,” “right,” and perspectiveviews are provided and labeled on the drawings. The terms “left,”“right,” “front” and “back” are used for description purposes only todistinguish views from 90 degree intervals around the propeller, but asa circular device, the terms have no significance. FIGS. 18A-G depict anillustrative embodiment of a propeller with a high rake value for intakeportion of the blade. FIGS. 19A-G depict a further illustrativeembodiment of a propeller with a high rake value for intake and exhaust.FIGS. 20A-I depict an inboard propeller. FIGS. 21A-G depict a propellerwith a through hub exhaust for an outboard motor.

Various embodiments of the invention have been described, each having adifferent combination of elements. The invention is not limited to thespecific embodiments disclosed, and may include different combinationsof the elements disclosed or omission of some elements and theequivalents of such structures.

While the invention has been described by illustrative embodiments,additional advantages and modifications will occur to those skilled inthe art. Therefore, the invention in its broader aspects is not limitedto specific details shown and described herein. Modifications, forexample, the number of blades and curvature of the blades, may be madewithout departing from the spirit and scope of the invention.Accordingly, it is intended that the invention not be limited to thespecific illustrative embodiments, but be interpreted within the fullscope of the appended claims and their equivalents.

The invention claimed is:
 1. A propeller for use with fluids, thepropeller provided to propel an object or person or to move the fluid,the propeller comprising: a plurality of asymmetrical blades; arotational axis; the plurality of blades extending outward from therotational axis and disposed around the rotational axis; each blade ofthe plurality of blades forming a loop and having an intake portion, andexhaust portion and a tip portion extending radially outward from therotational axis; the loop of each blade having an intake root and anexhaust root, and a gap between the intake root and the exhaust root;wherein the propeller has a configuration to generate non-axial lift andnon-axial fluid flow and to redirect the non-axial fluid flow to axialfluid flow, wherein the configuration includes: throughout at least aportion of the tip portion of the blades of the plurality of bladesbefore a 90 degree roll and toward the intake portion of the tipsection, a distance (N) to a nose of a cross-section as measuredperpendicularly from the rotational axis is greater than a distance (T)to a tail of the cross-section as measured perpendicularly from therotational axis, wherein the cross-section is taken from a fore locationview of the propeller along the rotational axis and perpendicularly tothe rotational axis; and each blade of the plurality of blades furthercomprising 80% of the tip portion of the blades having a roll value ofless than 90 degrees and N>T for the same 80% of the tip portion.
 2. Thepropeller of claim 1 wherein the blades of the plurality of blades areconfigured so the average non-axial lift is the greatest in the tipportion as compared to either the intake portion or the exhaust portionand the intake portion is 0-45% of the blades of the plurality of bladesand the tip portion is 30%-75% of the blades of the plurality of blades.3. The propeller of claim 1 wherein rake of the blades of the pluralityof blades is increasingly negative from the intake root through thefirst 30 percent to 40 percent of the each blade of the plurality ofblades, then increases for the next 10 percent to 15 percent of theblade until it reaches positive values and continues to increase for anadditional 20 percent to 40 percent of each blade of the plurality ofblades and then levels off for the remainder of each blade of theplurality of blades or decreases.
 4. The propeller of claim 1 whereinthe average pitch angle of the exhaust portion of the blades of theplurality of blades is greater than the average pitch of the intakeportion.
 5. The propeller of claim 1 wherein the blades of the pluralityof blades have the intake root and the exhaust root, and wherein thevalue of rake at the intake root position of the blades is less than thevalue of rake at the exhaust root position resulting in a gap betweenthe intake root and the exhaust root.
 6. The propeller of claim 1wherein a transition from the intake portion to the tip portion occurswhen the amount of non-axial lift produced by a given parameter sectionof each blade of the plurality of blades is greater than the axial liftproduced.
 7. The propeller of claim 1 wherein the blades of theplurality of blades have the intake root and the exhaust root, andwherein rake values of the blades of the plurality of blades decreasefrom the intake root and in the intake portion of the blades of theplurality of blades and increase in the exhaust portion of the blades.8. A device having the propeller according to claim 1 from the groupconsisting of jet engines, propulsors, shrouded propellers, encasedpropellers, impellers, aircraft, watercraft, turbines, including windturbines, cooling devices, heating devices, automobile engines, unmannedaerial vehicles, turbofans (hydrojets), air circulation devices,compressors, and pump jets.